MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.05 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh108-il-1000000.txt Download as CSV file: xf-mh108-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 108 11.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8010 0.15437 0.15261 0.0386 1.0000 0.0042
-16.250 -0.8715 0.13014 0.12811 0.0257 1.0000 0.0039
-16.000 -0.9027 0.11784 0.11568 0.0188 1.0000 0.0038
-15.750 -0.9354 0.10601 0.10370 0.0121 1.0000 0.0037
-15.500 -0.9638 0.09585 0.09339 0.0062 1.0000 0.0036
-15.250 -0.9889 0.08678 0.08421 0.0010 1.0000 0.0036
-15.000 -1.0180 0.07719 0.07447 -0.0047 1.0000 0.0035
-14.750 -1.0451 0.06814 0.06526 -0.0101 1.0000 0.0035
-14.500 -1.0692 0.05975 0.05671 -0.0155 1.0000 0.0035
-14.250 -1.0882 0.05247 0.04927 -0.0203 1.0000 0.0035
-14.000 -1.1020 0.04655 0.04319 -0.0241 1.0000 0.0034
-13.750 -1.1153 0.04152 0.03799 -0.0268 1.0000 0.0034
-13.500 -1.1255 0.03769 0.03402 -0.0279 1.0000 0.0035
-13.250 -1.1344 0.03463 0.03083 -0.0277 1.0000 0.0035
-13.000 -1.1404 0.03226 0.02831 -0.0263 1.0000 0.0035
-12.750 -1.1454 0.03027 0.02619 -0.0241 1.0000 0.0035
-12.500 -1.1474 0.02867 0.02449 -0.0214 1.0000 0.0035
-12.250 -1.1485 0.02724 0.02293 -0.0181 1.0000 0.0035
-12.000 -1.1468 0.02602 0.02160 -0.0148 1.0000 0.0036
-11.750 -1.1391 0.02482 0.02030 -0.0123 1.0000 0.0037
-11.500 -1.1281 0.02367 0.01904 -0.0103 1.0000 0.0037
-11.250 -1.1150 0.02260 0.01787 -0.0084 1.0000 0.0037
-11.000 -1.1000 0.02161 0.01678 -0.0067 1.0000 0.0039
-10.750 -1.0842 0.02062 0.01569 -0.0051 1.0000 0.0039
-10.500 -1.0666 0.01974 0.01471 -0.0036 1.0000 0.0040
-10.250 -1.0481 0.01890 0.01379 -0.0023 1.0000 0.0041
-10.000 -1.0283 0.01817 0.01298 -0.0011 1.0000 0.0044
-9.750 -1.0082 0.01742 0.01216 0.0001 1.0000 0.0044
-9.500 -0.9862 0.01686 0.01153 0.0011 1.0000 0.0046
-9.250 -0.9679 0.01584 0.01040 0.0026 1.0000 0.0049
-9.000 -0.9476 0.01504 0.00953 0.0038 1.0000 0.0053
-8.750 -0.9251 0.01447 0.00891 0.0048 1.0000 0.0056
-8.500 -0.9019 0.01398 0.00837 0.0056 1.0000 0.0059
-8.250 -0.8785 0.01350 0.00785 0.0065 1.0000 0.0063
-8.000 -0.8546 0.01309 0.00740 0.0073 1.0000 0.0067
-7.750 -0.8324 0.01245 0.00670 0.0084 1.0000 0.0077
-7.500 -0.8088 0.01201 0.00624 0.0092 1.0000 0.0089
-7.250 -0.7856 0.01153 0.00574 0.0102 1.0000 0.0111
-7.000 -0.7627 0.01104 0.00527 0.0112 1.0000 0.0161
-6.750 -0.7397 0.01061 0.00489 0.0122 1.0000 0.0236
-6.500 -0.7168 0.01021 0.00456 0.0133 1.0000 0.0326
-6.250 -0.6793 0.00977 0.00422 0.0111 0.9840 0.0455
-6.000 -0.6352 0.00942 0.00389 0.0076 0.9259 0.0596
-5.750 -0.6125 0.00931 0.00363 0.0090 0.8598 0.0708
-5.500 -0.5888 0.00918 0.00340 0.0100 0.8170 0.0834
-5.250 -0.5641 0.00902 0.00319 0.0108 0.7817 0.0973
-5.000 -0.5388 0.00886 0.00298 0.0114 0.7507 0.1128
-4.750 -0.5133 0.00867 0.00278 0.0120 0.7234 0.1317
-4.500 -0.4874 0.00850 0.00260 0.0124 0.6995 0.1500
-4.250 -0.4612 0.00835 0.00243 0.0129 0.6762 0.1676
-4.000 -0.4347 0.00823 0.00228 0.0133 0.6537 0.1847
-3.750 -0.4084 0.00807 0.00213 0.0137 0.6327 0.2058
-3.250 -0.3552 0.00779 0.00187 0.0144 0.5958 0.2501
-3.000 -0.3285 0.00766 0.00176 0.0147 0.5778 0.2744
-2.750 -0.3018 0.00753 0.00165 0.0150 0.5602 0.3007
-2.500 -0.2751 0.00740 0.00156 0.0154 0.5434 0.3288
-2.250 -0.2484 0.00728 0.00148 0.0157 0.5280 0.3580
-2.000 -0.2215 0.00717 0.00140 0.0160 0.5133 0.3858
-1.750 -0.1948 0.00705 0.00134 0.0163 0.4988 0.4190
-1.500 -0.1682 0.00693 0.00128 0.0167 0.4845 0.4526
-1.250 -0.1415 0.00682 0.00123 0.0170 0.4705 0.4861
-1.000 -0.1149 0.00672 0.00119 0.0174 0.4578 0.5212
-0.750 -0.0886 0.00660 0.00116 0.0178 0.4457 0.5610
-0.500 -0.0625 0.00648 0.00113 0.0183 0.4340 0.6038
-0.250 -0.0366 0.00637 0.00112 0.0188 0.4222 0.6469
0.000 -0.0108 0.00626 0.00111 0.0194 0.4109 0.6900
0.250 0.0148 0.00616 0.00112 0.0200 0.4005 0.7335
0.500 0.0402 0.00608 0.00114 0.0208 0.3907 0.7752
0.750 0.0659 0.00600 0.00116 0.0215 0.3814 0.8141
1.000 0.0919 0.00596 0.00121 0.0221 0.3725 0.8507
1.250 0.1188 0.00596 0.00126 0.0226 0.3632 0.8831
1.500 0.1477 0.00597 0.00133 0.0227 0.3554 0.9109
1.750 0.1801 0.00607 0.00142 0.0219 0.3468 0.9312
2.000 0.2145 0.00617 0.00151 0.0208 0.3390 0.9454
2.250 0.2473 0.00631 0.00161 0.0199 0.3314 0.9562
2.500 0.2819 0.00643 0.00171 0.0186 0.3245 0.9634
2.750 0.3139 0.00658 0.00181 0.0179 0.3175 0.9699
3.000 0.3521 0.00669 0.00190 0.0158 0.3113 0.9726
3.250 0.3880 0.00685 0.00201 0.0142 0.3044 0.9762
3.500 0.4183 0.00696 0.00212 0.0139 0.2994 0.9817
3.750 0.4569 0.00707 0.00220 0.0116 0.2932 0.9833
4.000 0.4944 0.00719 0.00230 0.0096 0.2874 0.9852
4.250 0.5312 0.00728 0.00238 0.0077 0.2818 0.9874
4.500 0.5665 0.00742 0.00249 0.0062 0.2754 0.9901
4.750 0.6008 0.00751 0.00259 0.0049 0.2706 0.9928
5.000 0.6367 0.00761 0.00267 0.0032 0.2643 0.9945
5.250 0.6738 0.00771 0.00276 0.0012 0.2584 0.9963
5.500 0.7119 0.00778 0.00283 -0.0010 0.2516 0.9984
5.750 0.7478 0.00790 0.00294 -0.0028 0.2449 1.0000
6.000 0.7723 0.00797 0.00303 -0.0021 0.2389 1.0000
6.250 0.7963 0.00813 0.00316 -0.0014 0.2314 1.0000
6.500 0.8208 0.00822 0.00328 -0.0007 0.2251 1.0000
6.750 0.8448 0.00839 0.00342 0.0001 0.2161 1.0000
7.000 0.8689 0.00856 0.00357 0.0008 0.2063 1.0000
7.250 0.8929 0.00875 0.00376 0.0015 0.1961 1.0000
7.500 0.9165 0.00899 0.00396 0.0023 0.1844 1.0000
7.750 0.9396 0.00928 0.00420 0.0031 0.1697 1.0000
8.000 0.9624 0.00960 0.00447 0.0039 0.1560 1.0000
8.250 0.9853 0.00992 0.00476 0.0048 0.1448 1.0000
8.500 1.0077 0.01028 0.00508 0.0056 0.1330 1.0000
8.750 1.0298 0.01068 0.00543 0.0065 0.1202 1.0000
9.000 1.0515 0.01110 0.00579 0.0075 0.1077 1.0000
9.250 1.0731 0.01153 0.00618 0.0085 0.0963 1.0000
9.500 1.0940 0.01201 0.00660 0.0095 0.0839 1.0000
9.750 1.1148 0.01249 0.00704 0.0105 0.0732 1.0000
10.000 1.1351 0.01300 0.00751 0.0116 0.0626 1.0000
10.250 1.1554 0.01350 0.00799 0.0127 0.0543 1.0000
10.500 1.1747 0.01407 0.00852 0.0139 0.0458 1.0000
10.750 1.1931 0.01470 0.00912 0.0152 0.0379 1.0000
11.000 1.2116 0.01530 0.00971 0.0165 0.0320 1.0000
11.250 1.2293 0.01595 0.01034 0.0178 0.0261 1.0000
11.500 1.2459 0.01665 0.01105 0.0192 0.0215 1.0000
11.750 1.2617 0.01738 0.01178 0.0207 0.0178 1.0000
12.000 1.2771 0.01810 0.01253 0.0223 0.0146 1.0000
12.250 1.2902 0.01893 0.01338 0.0240 0.0117 1.0000
12.500 1.3017 0.01982 0.01429 0.0259 0.0096 1.0000
12.750 1.3116 0.02073 0.01525 0.0279 0.0079 1.0000
13.000 1.3169 0.02169 0.01626 0.0306 0.0071 1.0000
13.250 1.3127 0.02297 0.01762 0.0342 0.0061 1.0000
13.500 1.3159 0.02422 0.01895 0.0359 0.0056 1.0000
13.750 1.3169 0.02600 0.02082 0.0367 0.0053 1.0000
14.000 1.3136 0.02870 0.02363 0.0365 0.0047 1.0000
14.250 1.3028 0.03283 0.02790 0.0348 0.0043 1.0000
14.500 1.3016 0.03609 0.03128 0.0334 0.0041 1.0000
14.750 1.2976 0.03981 0.03511 0.0317 0.0040 1.0000
15.000 1.2865 0.04449 0.03991 0.0295 0.0042 1.0000
15.250 1.2793 0.04864 0.04417 0.0277 0.0039 1.0000
15.500 1.2645 0.05382 0.04947 0.0254 0.0039 1.0000
15.750 1.2531 0.05855 0.05429 0.0235 0.0036 1.0000
16.000 1.2339 0.06439 0.06025 0.0210 0.0035 1.0000
16.250 1.2166 0.07003 0.06600 0.0186 0.0036 1.0000
16.500 1.2021 0.07551 0.07158 0.0162 0.0036 1.0000
16.750 1.1849 0.08152 0.07769 0.0135 0.0035 1.0000
17.000 1.1718 0.08701 0.08328 0.0111 0.0037 1.0000
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Polar data table (+)
Polar graphs
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